Dynamics & Controls PDR 2 Team “Canard” October 19, 2006

Overview from Previous Presentation Overview – Stability Longitudinal Stability Center of Gravity Location Tail / Elevator Sizing Trim Diagram / Desired Static Margin Lateral-Directional Stability Vertical Tail Sizing with X-Plot Rudder Size / Dihedral Angle Ailerons Sizing & Location Aircraft Transfer Functions Pitch Rate to Elevator Roll Rate to Aileron Yaw Rate to Rudder Overview from Previous Presentation AAE 451 Team 1

Longitudinal Stability… AAE 451 Team 1

Longitudinal Stability – Location of CG As initial assumption MATLAB Code used to optimize position of CG Initial assumption proved to work well Static Margin at desired location is: Chosen CG Location: Location of Forward CG: AAE 451 Team 1

Longitudinal Stability – Horizontal Tail Sizing Tail Sized using Class I Method (X-Plot) Initial Tail Size: Size @10% Static margin Size @18% Static margin x2 initial size!!.. Increase of Drag Tail size set up @ 15% margin AAE 451 Team 1

Longitudinal Stability – Elevator Sizing Elevator sized using Historical Data Our Tail volume ratio is: With Surface Ratio of: Flap Efficiency Factor: AAE 451 Team 1

Longitudinal Stability – Trim Diagram AAE 451 Team 1

Lateral Stability – Directional Control Vertical Tail Sizing Maximum Yaw Moment Coefficient Best Vertical Tail Area Range of 1% difference from Minimum Side Force Coefficient AAE 451 Team 1

Lateral Stability – Directional Control Rudder Sizing Historical Data of Homebuilt Aircraft Wing Area Vertical Tail Area Rudder Area found by using the corresponding average ratio Rudder Area AAE 451 Team 1

Lateral Stability – Lateral Control The Weathercock Stability Required Rudder Deflection angle to trim at a given sidewash angle The Side-Force Coefficient: The Yawning Moment Coefficient: The Yawning Moment due to Rudder Deflection AAE 451 Team 1

Dynamic Stability… AAE 451 Team 1

Aircraft Systems Transfer Functions Pitch Rate To Elevator AAE 451 Team 1

Aircraft Systems Transfer Functions Yaw Rate To Rudder AAE 451 Team 1

Aircraft Systems Transfer Functions Roll Rate To Aileron AAE 451 Team 1

Compensated System Gain: -0.412 Dutch Roll: 0.96 AAE 451 Team 1

Control System Root Locus General Block Diagram + Servo Aircraft - Gyro AAE 451 Team 1

Rate Gyro Procedure for setting the rate gyro: 1. Static Test -Dial in the gain -Perturb the aircraft -Make sure the rudder deflects to counter the yaw 2. Flight Test -Select one person to be the gain setter -Test the gain in flight -Insure safe recovery altitude AAE 451 Team 1

Questions?... Comments?... Concerns?... Thank you!!!! AAE 451 Team 1